Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

HAM-STD HS1-430 AIRFOIL (hs1430-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-430 AIRFOIL (hs1430-il)
Reynolds number: 500,000
Max Cl/Cd: 27.41 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1430-il-500000.txt
Download as CSV file: xf-hs1430-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-430 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.1689   0.07106   0.06546  -0.1054   0.9888   0.1171
 -19.500  -1.1764   0.06791   0.06222  -0.1052   0.9872   0.1183
 -19.250  -1.1805   0.06487   0.05907  -0.1054   0.9858   0.1194
 -19.000  -1.1821   0.06199   0.05605  -0.1058   0.9844   0.1204
 -18.750  -1.1766   0.05987   0.05396  -0.1060   0.9832   0.1219
 -18.500  -1.1698   0.05773   0.05181  -0.1066   0.9820   0.1232
 -18.250  -1.1612   0.05551   0.04956  -0.1075   0.9808   0.1244
 -18.000  -1.1502   0.05346   0.04746  -0.1086   0.9798   0.1258
 -17.750  -1.1389   0.05148   0.04540  -0.1096   0.9789   0.1272
 -17.500  -1.1271   0.04961   0.04344  -0.1105   0.9781   0.1286
 -17.250  -1.1102   0.04765   0.04137  -0.1124   0.9773   0.1298
 -17.000  -1.0893   0.04592   0.03966  -0.1144   0.9765   0.1316
 -16.750  -1.0647   0.04431   0.03805  -0.1169   0.9758   0.1332
 -16.500  -1.0682   0.04303   0.03675  -0.1136   0.9708   0.1343
 -16.250  -1.0515   0.04163   0.03530  -0.1142   0.9684   0.1358
 -16.000  -1.0324   0.04027   0.03389  -0.1151   0.9669   0.1373
 -15.750  -1.0127   0.03892   0.03246  -0.1162   0.9656   0.1388
 -15.500  -0.9905   0.03763   0.03107  -0.1176   0.9645   0.1401
 -15.250  -0.9663   0.03639   0.02988  -0.1191   0.9638   0.1420
 -15.000  -0.9412   0.03522   0.02871  -0.1208   0.9631   0.1436
 -14.750  -0.9136   0.03412   0.02758  -0.1228   0.9625   0.1454
 -14.500  -0.8858   0.03302   0.02644  -0.1248   0.9620   0.1472
 -14.250  -0.8965   0.03255   0.02593  -0.1185   0.9550   0.1482
 -14.000  -0.8764   0.03166   0.02496  -0.1187   0.9534   0.1496
 -13.750  -0.8519   0.03073   0.02397  -0.1197   0.9523   0.1511
 -13.500  -0.8242   0.02979   0.02309  -0.1211   0.9515   0.1532
 -13.250  -0.7964   0.02888   0.02218  -0.1225   0.9507   0.1550
 -13.000  -0.7703   0.02803   0.02132  -0.1235   0.9498   0.1569
 -12.750  -0.7431   0.02722   0.02048  -0.1246   0.9489   0.1587
 -12.500  -0.7406   0.02687   0.02009  -0.1204   0.9435   0.1600
 -12.250  -0.7211   0.02623   0.01937  -0.1198   0.9409   0.1614
 -12.000  -0.6934   0.02541   0.01858  -0.1207   0.9393   0.1636
 -11.750  -0.6672   0.02466   0.01787  -0.1213   0.9379   0.1657
 -11.500  -0.6404   0.02398   0.01720  -0.1220   0.9366   0.1676
 -11.250  -0.6338   0.02366   0.01688  -0.1184   0.9307   0.1690
 -11.000  -0.6126   0.02313   0.01632  -0.1177   0.9276   0.1709
 -10.750  -0.5863   0.02257   0.01571  -0.1181   0.9255   0.1727
 -10.500  -0.5656   0.02206   0.01520  -0.1172   0.9219   0.1745
 -10.250  -0.5457   0.02154   0.01472  -0.1162   0.9177   0.1764
 -10.000  -0.5177   0.02097   0.01415  -0.1168   0.9148   0.1782
  -9.750  -0.5032   0.02069   0.01386  -0.1144   0.9075   0.1799
  -9.500  -0.4897   0.02043   0.01359  -0.1118   0.8995   0.1816
  -9.250  -0.4836   0.02026   0.01338  -0.1076   0.8886   0.1831
  -9.000  -0.4571   0.01984   0.01290  -0.1076   0.8812   0.1849
  -8.750  -0.4345   0.01941   0.01246  -0.1069   0.8709   0.1867
  -8.500  -0.4086   0.01899   0.01204  -0.1068   0.8590   0.1884
  -8.250  -0.3799   0.01861   0.01161  -0.1073   0.8439   0.1904
  -8.000  -0.3512   0.01828   0.01118  -0.1078   0.8253   0.1925
  -7.750  -0.3264   0.01807   0.01082  -0.1074   0.8023   0.1946
  -7.500  -0.3068   0.01797   0.01055  -0.1058   0.7802   0.1964
  -7.250  -0.2908   0.01792   0.01036  -0.1034   0.7639   0.1977
  -7.000  -0.2725   0.01776   0.01011  -0.1017   0.7495   0.1995
  -6.750  -0.2551   0.01754   0.00989  -0.0997   0.7386   0.2017
  -6.500  -0.2410   0.01745   0.00976  -0.0970   0.7276   0.2035
  -6.250  -0.2258   0.01739   0.00966  -0.0945   0.7172   0.2053
  -6.000  -0.2096   0.01735   0.00957  -0.0921   0.7040   0.2073
  -5.750  -0.1944   0.01735   0.00948  -0.0895   0.6905   0.2093
  -5.500  -0.1787   0.01734   0.00940  -0.0870   0.6770   0.2111
  -5.250  -0.1640   0.01737   0.00933  -0.0843   0.6648   0.2125
  -5.000  -0.1489   0.01717   0.00912  -0.0817   0.6520   0.2150
  -4.750  -0.1420   0.01708   0.00900  -0.0773   0.6398   0.2174
  -4.500  -0.1305   0.01701   0.00893  -0.0739   0.6275   0.2195
  -4.250  -0.1229   0.01706   0.00891  -0.0696   0.6126   0.2215
  -4.000  -0.1146   0.01714   0.00891  -0.0655   0.5909   0.2235
  -3.750  -0.1048   0.01727   0.00893  -0.0617   0.5659   0.2255
  -3.500  -0.1016   0.01759   0.00905  -0.0566   0.5254   0.2272
  -3.250  -0.1026   0.01814   0.00930  -0.0507   0.4694   0.2285
  -3.000  -0.0982   0.01864   0.00953  -0.0461   0.4184   0.2300
  -2.750  -0.1021   0.01931   0.00984  -0.0400   0.3325   0.2328
  -2.500  -0.0914   0.01964   0.01001  -0.0369   0.2962   0.2356
  -2.250  -0.0741   0.01979   0.01012  -0.0349   0.2831   0.2383
  -2.000  -0.0551   0.01994   0.01023  -0.0334   0.2755   0.2409
  -1.750  -0.0348   0.02006   0.01032  -0.0320   0.2707   0.2433
  -1.500  -0.0139   0.02020   0.01042  -0.0308   0.2672   0.2455
  -1.250   0.0069   0.02035   0.01054  -0.0296   0.2645   0.2473
  -1.000   0.0283   0.02049   0.01065  -0.0285   0.2627   0.2489
  -0.750   0.0487   0.02049   0.01067  -0.0273   0.2614   0.2528
  -0.500   0.0698   0.02055   0.01076  -0.0262   0.2602   0.2561
  -0.250   0.0912   0.02066   0.01089  -0.0252   0.2591   0.2589
   0.000   0.1124   0.02080   0.01103  -0.0241   0.2581   0.2615
   0.250   0.1336   0.02097   0.01120  -0.0231   0.2571   0.2642
   0.500   0.1549   0.02116   0.01138  -0.0221   0.2561   0.2666
   0.750   0.1761   0.02137   0.01158  -0.0211   0.2552   0.2687
   1.000   0.1971   0.02161   0.01180  -0.0200   0.2543   0.2703
   1.250   0.2177   0.02179   0.01200  -0.0190   0.2536   0.2744
   1.500   0.2382   0.02199   0.01223  -0.0179   0.2530   0.2790
   1.750   0.2583   0.02223   0.01250  -0.0168   0.2524   0.2835
   2.000   0.2788   0.02248   0.01278  -0.0158   0.2518   0.2886
   2.250   0.2999   0.02275   0.01306  -0.0149   0.2514   0.2942
   2.500   0.3210   0.02294   0.01333  -0.0141   0.2511   0.3063
   2.750   0.3418   0.02313   0.01362  -0.0132   0.2507   0.3251
   3.000   0.3616   0.02310   0.01391  -0.0123   0.2504   0.3902
   3.250   0.3777   0.02265   0.01424  -0.0107   0.2501   0.5721
   3.500   0.3961   0.02270   0.01469  -0.0093   0.2498   0.6650
   3.750   0.4166   0.02296   0.01511  -0.0084   0.2494   0.7072
   4.000   0.4375   0.02324   0.01553  -0.0075   0.2491   0.7406
   4.250   0.4579   0.02352   0.01600  -0.0064   0.2487   0.7778
   4.500   0.4764   0.02385   0.01663  -0.0048   0.2484   0.8377
   4.750   0.4953   0.02441   0.01738  -0.0031   0.2481   0.8946
   5.000   0.5154   0.02502   0.01803  -0.0018   0.2477   0.9232
   5.250   0.5370   0.02564   0.01868  -0.0010   0.2474   0.9395
   5.500   0.5577   0.02627   0.01931  -0.0001   0.2470   0.9525
   5.750   0.5842   0.02702   0.02005  -0.0005   0.2466   0.9625
   6.000   0.6092   0.02773   0.02074  -0.0005   0.2462   0.9709
   6.250   0.6471   0.02856   0.02156  -0.0036   0.2457   0.9745
   6.500   0.6862   0.02942   0.02240  -0.0069   0.2452   0.9773
   6.750   0.7228   0.03027   0.02323  -0.0097   0.2444   0.9805
   7.000   0.7556   0.03112   0.02405  -0.0118   0.2436   0.9842
   7.250   0.7828   0.03192   0.02483  -0.0126   0.2430   0.9880
   7.500   0.8169   0.03265   0.02554  -0.0150   0.2424   0.9891
   7.750   0.8511   0.03339   0.02625  -0.0175   0.2418   0.9905
   8.000   0.8871   0.03416   0.02698  -0.0203   0.2411   0.9921
   8.250   0.9219   0.03486   0.02766  -0.0229   0.2405   0.9939
   8.500   0.9534   0.03556   0.02835  -0.0248   0.2399   0.9956
   8.750   0.9834   0.03634   0.02916  -0.0265   0.2391   0.9974
   9.000   1.0139   0.03717   0.03000  -0.0284   0.2383   0.9991
   9.250   1.0380   0.03787   0.03072  -0.0289   0.2375   1.0000
   9.500   1.0490   0.03832   0.03117  -0.0268   0.2368   1.0000
   9.750   1.0600   0.03880   0.03167  -0.0247   0.2362   1.0000
  10.000   1.0704   0.03933   0.03220  -0.0226   0.2354   1.0000
  10.250   1.0818   0.03982   0.03269  -0.0206   0.2347   1.0000
  10.500   1.0939   0.04031   0.03318  -0.0187   0.2340   1.0000
  10.750   1.1057   0.04082   0.03369  -0.0169   0.2333   1.0000
  11.000   1.1176   0.04135   0.03421  -0.0151   0.2326   1.0000
  11.250   1.1304   0.04184   0.03469  -0.0134   0.2319   1.0000
  11.500   1.1448   0.04226   0.03509  -0.0120   0.2312   1.0000
  11.750   1.1623   0.04254   0.03532  -0.0109   0.2303   1.0000
  12.000   1.1742   0.04313   0.03595  -0.0093   0.2296   1.0000
  12.250   1.1832   0.04393   0.03679  -0.0074   0.2286   1.0000
  12.500   1.1936   0.04468   0.03758  -0.0057   0.2277   1.0000
  12.750   1.2054   0.04539   0.03831  -0.0042   0.2267   1.0000
  13.000   1.2181   0.04608   0.03902  -0.0029   0.2256   1.0000
  13.250   1.2313   0.04678   0.03973  -0.0018   0.2246   1.0000
  13.500   1.2449   0.04750   0.04044  -0.0007   0.2236   1.0000
  13.750   1.2605   0.04813   0.04105   0.0001   0.2226   1.0000
  14.000   1.2808   0.04846   0.04132   0.0004   0.2215   1.0000
  14.250   1.2945   0.04936   0.04226   0.0013   0.2204   1.0000
  14.500   1.3062   0.05048   0.04344   0.0021   0.2192   1.0000
  14.750   1.3187   0.05159   0.04459   0.0028   0.2179   1.0000
  15.000   1.3323   0.05264   0.04566   0.0033   0.2165   1.0000
  15.250   1.3487   0.05348   0.04648   0.0036   0.2152   1.0000
  15.500   1.3697   0.05394   0.04688   0.0036   0.2139   1.0000
  15.750   1.3903   0.05445   0.04736   0.0036   0.2126   1.0000
  16.000   1.3973   0.05616   0.04918   0.0044   0.2112   1.0000
  16.250   1.4081   0.05757   0.05064   0.0048   0.2096   1.0000
  16.500   1.4223   0.05870   0.05177   0.0051   0.2081   1.0000
  16.750   1.4423   0.05928   0.05231   0.0049   0.2068   1.0000
  17.000   1.4709   0.05907   0.05200   0.0043   0.2054   1.0000
  17.250   1.4666   0.06191   0.05502   0.0055   0.2039   1.0000
  17.500   1.4719   0.06392   0.05711   0.0060   0.2022   1.0000
  17.750   1.4824   0.06544   0.05867   0.0062   0.2007   1.0000
  18.000   1.4989   0.06638   0.05959   0.0061   0.1995   1.0000
  18.250   1.5188   0.06696   0.06013   0.0059   0.1983   1.0000
  18.500   1.5080   0.07071   0.06411   0.0068   0.1964   1.0000
  18.750   1.5088   0.07336   0.06688   0.0071   0.1945   1.0000
  19.000   1.5155   0.07542   0.06899   0.0071   0.1930   1.0000
  19.250   1.5242   0.07727   0.07086   0.0069   0.1918   1.0000
<< Back to HAM-STD HS1-430 AIRFOIL (hs1430-il)

Polar data table (+)

Polar graphs


<< Back to HAM-STD HS1-430 AIRFOIL (hs1430-il)